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1.发明申请公开(公告)号：US20190217947A1
公开(公告)日：2019-07-18
申请号：US16368442
申请日：2019-03-28
Applicant: Borealis Technical Limited
Inventor： Joseph J. Cox , Isaiah W. Cox , Jan Vana , Michael Spillias , Joseph Goldman
CPC classification number: B64C25/405 , B64D43/00 , B64F5/60 , Y02T50/823
Abstract: A cockpit control system and method for efficiently controlling ground travel in an aircraft equipped with engine-free electric taxi drive systems are provided. The cockpit control system is configured with a display that provides a maximum amount of information during aircraft ground movement with a minimal amount of input from and distraction to pilots or cockpit crew to facilitate essentially hands free operation and control of aircraft ground travel. System test and drive procedures ensure safe aircraft ground travel with the engine-free electric taxi system. Constant pilot hand or other input is not required to achieve safe and maximally efficient aircraft ground travel powered by the aircraft's engine-free electric taxi drive systems or, under selected defined conditions, by the aircraft's engines to achieve this maximum efficiency. The system may further be designed to be uninterruptible by unauthorized persons.
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公开(公告)号：US20190193845A1
公开(公告)日：2019-06-27
申请号：US16287839
申请日：2019-02-27
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： James MORRIS , Antonio COLOSIMO
CPC classification number: B64C25/445 , B60T8/00 , B60T8/1703 , B64C25/34 , B64C25/405 , Y02T50/823
Abstract: The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.
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公开(公告)号：US20180244375A1
公开(公告)日：2018-08-30
申请号：US15956220
申请日：2018-04-18
Applicant: Borealis Technical Limited
Inventor： Isaiah W. Cox , Joseph J. Cox
CPC classification number: B64C25/405 , B64F1/002 , F16D41/06 , F16D41/125 , F16D48/06 , F16D2500/10412 , F16D2500/10493 , F16D2500/30806 , F16D2500/3102 , F16D2500/3108 , F16D2500/31493 , Y02T50/823
Abstract: A clutch driven aircraft electric taxi system is provided with a clutch assembly designed to be automatically selectively engaged or disengaged as required to drive an aircraft autonomously during ground operations. The clutch assembly is mounted integrally with other electric taxi system components completely within an aircraft landing gear wheel and may be designed with one way overrunning or selectable clutch engagement capability in one or both rotational directions, preferably using an arrangement of ratcheting struts and clutch elements adapted specifically for use in an aircraft landing gear drive wheel environment. The clutch assembly may automatically disengage in response to predetermined defined conditions or operating parameters. A failsafe overrunning capability ensures that the clutch assembly will not engage taxi system drive components so that an aircraft's wheel will not be driven during aircraft operation when safety considerations dictate that the aircraft electric taxi system should not be engaged.
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公开(公告)号：US20180201366A1
公开(公告)日：2018-07-19
申请号：US15889910
申请日：2018-02-06
Applicant: Borealis Technical Limited
Inventor： Isaiah W. Cox , Rodney T. Cox
CPC classification number: B64C25/405 , B64F1/00 , B64F1/3055 , Y02T50/823
Abstract: A method for reducing aircraft turnaround time by improving airport ramp safety is provided. The method minimizes the time interval between an aircraft's landing and takeoff by independently moving the aircraft on the ground without the aircraft's engines by eliminating hazards from jet blast, the possibility of engine ingestion, and the time previously required to wait in the gate area upon arrival or at departure until jet blast or engine ingestion did not pose a danger. Turnaround time is further reduced by providing an onboard driver controllable to drive at least one of the aircraft's wheels between landing and takeoff, thereby eliminating the need for a tow vehicle and the time required to move the aircraft with a tow vehicle.
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公开(公告)号：US20180170528A1
公开(公告)日：2018-06-21
申请号：US15737256
申请日：2016-06-16
Applicant: SAFRAN ELECTRONICS & DEFENSE , SAFRAN ELECTRICAL & POWER
Inventor： Serge ROQUES , Francois GUILLOT
CPC classification number: B64C25/24 , B64C25/34 , B64C25/405 , B64C25/42 , B64C25/50 , B64C39/024 , Y02T50/823
Abstract: The invention relates to an aircraft landing gear (2) comprising:—a leg (6) having a first leg portion (8) that can be pivotably connected to a load-bearing structure of the aircraft (1) in order for the landing gear (2) to be deployed and retracted, and a second leg portion (9) that is rotatable in relation to the first leg portion (8);—a wheel (13, 14) that is rotatable in relation to the second leg portion (9), and an electric motor (15, 16) that can rotate the wheel (13, 14) in relation to the second leg portion (9);—a transmission mechanism (17) designed to selectively transmit torque generated by the electric motor (15, 16) to the wheel (13, 14) in order to rotate the wheel in relation to the second leg portion (9) or to the second leg portion (9) in order to rotate the second leg portion (9) in relation to the first leg portion (8).
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Patent Agency Ranking
公开(公告)号：US09975626B2
公开(公告)日：2018-05-22
申请号：US14932342
申请日：2015-11-04
Applicant: Borealis Technical Limited
Inventor： Isaiah W. Cox , Joseph J. Cox
CPC classification number: B64C25/405 , B64F1/002 , F16D41/06 , F16D41/125 , F16D48/00 , Y02T50/823
Abstract: A clutch driven aircraft electric taxi system is provided with a clutch assembly designed to be automatically selectively engaged or disengaged as required to drive an aircraft autonomously during ground operations. The clutch assembly is mounted integrally with other electric taxi system components completely within an aircraft landing gear wheel and may be designed with one way overrunning or selectable clutch engagement capability in one or both rotational directions, preferably using an arrangement of ratcheting struts and clutch elements adapted specifically for use in an aircraft landing gear drive wheel environment. The clutch assembly may automatically disengage in response to predetermined defined conditions or operating parameters. A failsafe overrunning capability ensures that the clutch assembly will not engage taxi system drive components so that an aircraft's wheel will not be driven during aircraft operation when safety considerations dictate that the aircraft electric taxi system should not be engaged.
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公开(公告)号：US20180118333A1
公开(公告)日：2018-05-03
申请号：US15852725
申请日：2017-12-22
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： Arnaud DIDEY
CPC classification number: B64C25/405 , F16H1/006 , F16H1/06 , F16H1/26 , Y02T50/823
Abstract: A drive system for an aircraft landing gear, the drive system including a pinion gear, a drive shaft arranged to rotate the pinion gear about a drive axis, a driven gear arranged to mesh with the pinion gear to be rotatable by the pinion gear, the driven gear being connectable to a wheel of the landing gear to be capable of rotating the wheel about a wheel axis; and a flexible interface. The flexible interface includes a plurality of driven gear coupling members, each driven gear coupling member having a first connection portion attached to the driven gear, a second connection portion adapted to be attached to the wheel at an offset distance from the wheel axis, and a joint between the first connection portion and the second connection portion, the joint permitting relative movement between the first connection portion and the second connection portion.
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公开(公告)号：US09914530B2
公开(公告)日：2018-03-13
申请号：US13416614
申请日：2012-03-09
Applicant: Isaiah Watas Cox , Rodney T. Cox , Aaron Z. Sichel
Inventor： Isaiah Watas Cox , Rodney T. Cox , Aaron Z. Sichel
CPC classification number: B64C25/405 , B64F1/00 , B64F1/3055 , Y02T50/823
Abstract: A method for reducing aircraft turnaround time by improving airport ramp safety is provided. The method minimizes the time interval between an aircraft's landing and takeoff by independently moving the aircraft on the ground without the aircraft's engines by eliminating hazards from jet blast, the possibility of engine ingestion, and the time previously required to wait in the gate area upon arrival or at departure until jet blast or engine ingestion did not pose a danger. Turnaround time is further reduced by providing an onboard driver controllable to drive at least one of the aircraft's wheels between landing and takeoff, thereby eliminating the need for a tow vehicle and the time required to move the aircraft with a tow vehicle.
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公开(公告)号：US09862484B2
公开(公告)日：2018-01-09
申请号：US14868803
申请日：2015-09-29
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Mathieu Daffos
CPC classification number: B64C25/405 , B64C25/34 , B64C25/42 , Y02T50/823
Abstract: An undercarriage having a wheel mounted on an axle (3), a brake and a drive assembly. The brake comprises a torsion tube (9), friction members (11) mounted around the torsion tube, and at least one brake actuator (13) for selectively exerting a braking force on the friction members. The drive assembly is operative to drive rotation of the wheel and comprises an electric motor (14) that is connected to a rim (5) of the wheel (4) by a coupler member (15). The coupler member extends at least in part around the axle (3) between the axle and the torsion tube (9) of the brake.
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公开(公告)号：US09849972B2
公开(公告)日：2017-12-26
申请号：US14912692
申请日：2014-07-21
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： James Morris , Antonio Colosimo
CPC classification number: B64C25/445 , B60T8/00 , B60T8/1703 , B64C25/34 , B64C25/405 , Y02T50/823
Abstract: The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback maneuver, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.
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